Air/Fuel Supply System for Use in a Gas Turbine Engine

An air/fuel supply system for use in a combustor assembly of a gas turbine engine, the air/fuel supply system comprising:

• a fuel injector comprising:
• a main body having an inlet end and an outlet end and defining a longitudinal axis defining a longitudinal direction of said fuel injector and extending between said outlet end and said inlet end, said main body comprising a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet, wherein said plurality of air/fuel passages is configured to minimize excess wall thickness between adjacent air/fuel passages of said plurality of air/fuel passages;
• and
• a fuel supply structure in said main body extending in said longitudinal direction, said fuel supply structure including at least one fuel inlet that receives fuel from a source of fuel and a plurality of fuel outlets, each said fuel outlet communicating with and supplying fuel to at least one of said air/fuel passages, wherein said fuel supply structure includes isolated fuel distribution passages that individually deliver respective portions of fuel from said fuel supply structure to each of said air fuel passages;
• wherein:
• air passing through each said air/fuel passage is mixed with fuel from at least one of said fuel outlets, said mixing occurring within each said air/fuel passage to produce an air/fuel mixture within each air/fuel passage, said air/fuel mixture within each said air/fuel passage exiting said outlet end of said main body through a respective air/fuel passage outlet.